
[Federal Register Volume 82, Number 49 (Wednesday, March 15, 2017)]
[Rules and Regulations]
[Page 13752]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-05000]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 21

[Docket No. FAA-2016-9452]


Airworthiness Criteria: Glider Design Criteria for Stemme AG 
Model Stemme S12 Powered Glider

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Airworthiness design criteria.

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SUMMARY: These airworthiness criteria are issued for the Stemme AG 
model Stemme S12 powered glider. The Administrator finds the design 
criteria, which make up the certification basis for the Stemme S12, 
acceptable.

DATES: These airworthiness design criteria are effective April 14, 
2017.

FOR FURTHER INFORMATION CONTACT: Mr. Jim Rutherford, Federal Aviation 
Administration, Small Airplane Directorate, Aircraft Certification 
Service, 901 Locust, Room 301, Kansas City, MO 64106, telephone (816) 
329-4165, facsimile (816) 329-4090.

SUPPLEMENTARY INFORMATION: 

Background

    On January 08, 2016, Stemme AG submitted an application for type 
validation of the Stemme S12 in accordance with the Technical 
Implementation Procedures for Airworthiness and Environmental 
Certification Between the FAA and the European Aviation Safety Agency 
(EASA), Revision 5, dated September 15, 2015. The Stemme S12 is a two-
seat, self-launching, powered glider with a liquid cooled, turbocharged 
engine mounted in the center fuselage, an indirect drive shaft, and a 
fully-foldable, variable-pitch composite propeller in the nose. It is 
constructed from glass and carbon fiber reinforced composites, features 
a conventional T-type tailplane, and has a retractable main landing 
gear. The glider has a maximum weight of 1,984 pounds (900 kilograms) 
and may be equipped with an optional dual-axis autopilot system. EASA 
type certificated the Stemme S12 under Type Certificate Number (No.) 
EASA.A.054 on March 11, 2016. The associated EASA Type Certificate Data 
Sheet (TCDS) No. EASA.A.054 defined the certification basis Stemme AG 
submitted to the FAA for review and acceptance.
    The applicable requirements for glider certification in the United 
States can be found in FAA Advisory Circular (AC) 21.17-2A, ``Type 
Certification--Fixed-Wing Gliders (Sailplanes), Including Powered 
Gliders,'' dated February 10, 1993. AC 21.17-2A has been the basis for 
certification of gliders and powered gliders in the United States for 
many years. AC 21.17-2A states that applicants may utilize the Joint 
Aviation Requirements (JAR)-22, ``Sailplanes and Powered Sailplanes'', 
or another accepted airworthiness criteria, or a combination of both, 
as the accepted means for showing compliance for glider type 
certification.

Type Certification Basis

    The applicant Certification Basis is based on EASA Certification 
Specification (CS)-22, ``Sailplanes and Powered Sailplanes'', initial 
issue, dated November 14, 2003. In addition to CS-22 requirements, the 
applicant will comply with other requirements from the certification 
basis referenced in EASA TCDS No. EASA.A.054, including special 
conditions and equivalent safety findings.

Discussion of Comments

    Notice of proposed airworthiness design criteria for the Stemme AG 
Stemme S12 powered glider was published in the Federal Register on 
November 30, 2016 (81 FR 86296). No comments were received, therefore 
these airworthiness design criteria are adopted as proposed.

The Airworthiness Design Criteria

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the following airworthiness design criteria under the 
special class provision of 14 CFR 21.17(b) as part of the type 
certification basis for the Stemme AG Stemme S12 power glider:
    1. 14 CFR part 21, effective February 1, 1965, including amendments 
21-1 through 21-93 as applicable.
    2. EASA CS-22, initial issue, dated November 14, 2003.
    3. EASA Special Condition No. SC-A.22.1.01, ``Increase in maximum 
mass for sailplanes and powered sailplanes.''
    4. ``Preliminary Standard for the Substantiation of Indirect Drive 
Shafts in Power Plants of Powered Sailplanes Certified to JAR-22'' 
(with a modification for the Stemme AG model Stemme S 10), Luftfahrt-
Bundesamt (LBA) document number (no.) I231-87, issued August 05, 1988.
    5. Installation of a Dual-Axis Autopilot System, including--
     EASA CS-VLA (Very Light Aeroplanes) 1309, ``Equipment, 
systems, and installations''; initial issue, dated November 14, 2003; 
and
     EASA CS-23.1329, ``Automatic pilot system'', amendment 3, 
dated July 20, 2012.
    6. Drop Testing for Retractable Landing Gear (EASA equivalent 
safety findings) to include CS-VLA 725, ``Limit drop tests''; CS-VLA 
726, ``Ground load dynamic tests''; and CS-VLA 727, ``Reserve energy 
absorption''; initial issue dated November 14, 2003.
    7. ``Standards for Structural Substantiation of Sailplane and 
Powered Sailplane Parts Consisting of Glass or Carbon Fiber Reinforced 
Plastics'', LBA document no. I4-FVK/91, issued July 1991.
    8. ``Guideline for the analysis of the electrical system for 
powered sailplanes'', LBA document no. I334-MS 92, issued September 15, 
1992.
    9. The following kinds of operation are allowed: VFR-Day.
    10. Date of application for FAA Type Certificate: January 08, 2016.

    Issued in Kansas City, Missouri on January 23, 2017.
Mel Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-05000 Filed 3-14-17; 8:45 am]
 BILLING CODE 4910-13-P


